US4664338A - Projectile having extendable wings - Google Patents

Projectile having extendable wings Download PDF

Info

Publication number
US4664338A
US4664338A US06/772,247 US77224785A US4664338A US 4664338 A US4664338 A US 4664338A US 77224785 A US77224785 A US 77224785A US 4664338 A US4664338 A US 4664338A
Authority
US
United States
Prior art keywords
spar
projectile
wing
edge
nose
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
US06/772,247
Other languages
English (en)
Inventor
Raimar Steuer
Bernd Brieseck
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Diehl Verwaltungs Stiftung
Original Assignee
Diehl GmbH and Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from DE19833340501 external-priority patent/DE3340501C2/de
Application filed by Diehl GmbH and Co filed Critical Diehl GmbH and Co
Assigned to DIEHL GMBH & CO. reassignment DIEHL GMBH & CO. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: STEUER, RAIMAR
Application granted granted Critical
Publication of US4664338A publication Critical patent/US4664338A/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/146—Fabric fins, i.e. fins comprising at least one spar and a fin cover made of flexible sheet material

Definitions

  • the present invention relates to a projectile possessing extendable wings adapted to be pivoted radially outwardly of the projectile.
  • a projectile of that type has been previously proposed for large-calibered barrel-fired ammunition which can be guided by extendable wings or fins during the end phase of its flight.
  • each of these wings consist of a covering portion which is fastened to the projectile body itself, and with the covering being primarily tensioned by an internally extended strut arrangement, but with wing shape being determined by the inflating cushioning effect of the oncoming airflow.
  • the present invention provides for a projectile incorporating extendable wings or fins, with each wing or fin including a flexible covering and a tensioning device; for example, a strut arrangement, and with the wing or fin being displaceable from a retracted position prior to launch of the projectile to an outwardly extended position in which the applicable covering portion is tensioned by the tensioning device so as to thereby provide a stable, predetermined aerodynamically defined wing or fin configuration.
  • a tensioning device for example, a strut arrangement
  • a projectile having wings which can be pivoted outwardly from longitudinal recesses formed in the outer wall structure of the projectile, and wherein, in each instance, the wings comprise a strut arrangement and a covering adapted to be stretched thereby, and in which the covering, rearwardly of the leading edge of the wing, encompasses an aerodynamically profiled rigid nose spar which is hinged so as to be able to be swung forward laterally, with its inner end in or towards the front portion of the longitudinal recess.
  • the present invention thus provides a projectile which is equipped with space-saving or compact swing-wing structure, in which the aerodynamic wing effect can be constructionally predetermined and constitutes a significant improvement with respect to the practical applications thereof in contrast with current projectiles.
  • the strut arrangement for stretching the wing covering in the region of the aerodynamically-critical leading edge may incorporate rigid and geometrically particularly configured nose spar.
  • the covering essentially wraps itself around the spar such that the geometry of the self-supporting, and possibly hollow, portion of the wing covering when the wing is pivoted outwardly is predetermined to a considerably extent; in effect is apparently optimized.
  • a rigid profiled rear spar can be hinged to the outer end of the nose spar so as to, with respect to the surroundings of the trailing edge of the wing, constitute a defined cross-sectional geometry.
  • the rearward portion of the nose spar is preferably designed as a recess which is profiled in a U-shaped configuration open towards the rear. At least a portion of the remainder of the strut arrangement can be pivoted into the cavity when the wing is moved into its retracted position in the projectile body.
  • a root or base rib which is divided into two joined parts, and which is extendable through a knee hinge joint may be provided to extend along the body of the projectile; or alternatively the hinge on the base portion of the wing may be omitted to provide a simpler construction and kinematic operation.
  • a unitary rigid rocker arm which is hinged at its front end to the wing nose spar, needs to be pivoted out rearwardly with the nose spar arranged in the outwardly extended position.
  • a free rear end of the rocker arm swings out the rear spar (which is located behind the rocker arm prior to the wing being fully extended), and the rear spar thereby pivots in the opposite sense to the rocker arm as the wing is fully extended (in essence, opposite the direction of flight of the projectile) about its hinge at the outer end of the nose spar and against an elastic restoring force of the thereby stretched covering.
  • the arm can be profiled along its entire length so as to be highly resistant to distortion, with this aspect imparting an additional contribution to the possibility of introducing a force for the stretching of the covering (additional strength) and in the extended position produces a highly distortion-resistant wing.
  • FIG. 1 shows a schematic plan view of a wing or stabilizing fin for a projectile extended radially outwardly into the operational position, and shows the relative orientation of wing parts with a rear spar swung into a retracted position;
  • FIG. 2 shows a sectional view taken along line II--II in FIG. 1 in the plane of a base rib knee hinge joint with the rear spar swung in accordance with FIG. 1;
  • FIG. 3 shows a view similar to FIG. 1, but with the rear spar replaced by a bracing wire;
  • FIG. 4 shows a modified strut arrangement swung in from the rear into a nose spar of the wing, but without the wing covering which is stretched or tensioned thereby;
  • FIG. 5 shows the strut arrangement pursuant to FIG. 1 in an extended position
  • FIG. 6 shows the cross-sectional profile of a rocker arm taken along line III--III in FIG. 5 with transverse dimensions, shown on an enlarged scale;
  • FIG. 7 shows the cross-sectional profile of the rear spar taken along line IV--IV in FIG. 5.
  • a projectile 1 shown in a cut-away longitudinal sectional view in FIG. 1 has formed the periphery of its body 2, offset peripherally along the wall 3 thereof, at least two longitudinal recesses 4 which extend in an approximately axially-parallel orientation along the longitudinal direction of the body 2 (only one recess 4 is shown in the drawing).
  • the longitudinal recesses 4 serve to receive, in each instance, a wing or fin 5 in a folded (retracted) position.
  • the wing or fin 5 consists of a strut arrangement 6, which is encompassed by a covering 7, for example, of sail-cloth, which covering defines the upper and lower wing surface thereof when tensioned in the extended or outwardly pivoted position of the wing 5.
  • the strut arrangement 6 has a nose spar 8 which is optimized in its cross-section with respect to the lift factors; the leading edge 9 of the nose spar together with the adjoining wing surfaces 10 are surrounded by tautened covering 7 with the wing in the outwardly pivoted position.
  • the nose spar 8 is hinged to the fuselage 2 by means of a swivel hinge (pivot) 11 in the front region (view in the direction of flight of the projectile 1) of the longitudinal recess so as to be swingable laterally out beyond the peripheral boundary of the outer wall 3 of the projectile body.
  • adjusting elements such as a pyrotechnic element or spring-biased elements, possibly with the interposition of gear elements, can be connected in a force-fitted manner (operatively engaged) with a swivel or rocker shaft 12; in order to thereby during a specific flight phase of the projectile, for example, in a time-controlled or program-controlled manner, to pivot (extend) the wing 5 outwardly (initially retracted into its associated longitudinal recess 4), and to thereby ensure a stable flight behavior, suitably, more particularly for control during the end-phase of the flight of the projectile 1 over a specific time interval after firing from a weapon.
  • a further improvement in flight dynamics can be achieved when there is also provided in the surroundings of the trailing edge 13 a defined aerodynamically optimized cross-sectional geometry of the wing 5.
  • a rigid rear spar 14 which is profiled in an appropriately aerodynamically optimized manner is articulated by means of a hinge pin 16 to the free outer end of the wing 5 (which outer end can be outwardly pivoted).
  • the covering 7 which is subjected to the oncoming air flow thus extends level (smoothly) along the rigidly preset rearward wing surfaces 17 in a geometrically optimized manner.
  • the covering 7 Only in the generally triangular centre region between the two spars 8, 14 and the projectile fuselage 2 does the covering 7 extend in an unsupported manner; in regard to which this orientation is preset by the arching or curvature of the wing surfaces 10, from the leading edge 9 up to inclusive the trailing wing surfaces 17, as a result of which the covering 7 is tautened upon the wing 5 being outwardly pivoted; in effect, is aerodynamically optimized.
  • a base rib 18 extends along the projectile body 2, which can be retracted or held extended through a knee hinge joint 19.
  • Those parts of the base rib 18 which are respectively located on each side of the knee hinge joint 19, are hinged, on the one hand, in the region of the inner end 20 of the nose spar 8 and oppositely in the region of the inner end 21 of the rear spar 14. It can be suitable to also conduct the covering 7 about this two-part base rib 18; such that all three lateral edges of the triangular wing 15 are then geometrically defined by rigid structural parts, which further improves the capabilities for the aerodynamic optimization of the cross-sectional shape of the wing 5.
  • an adjusting member can be provided similar to that which acts on the nose-spar rocker shaft 12. It is more expedient to insert, for example by way of a stiff tension spring 29, a traction cable 30 between the base rib 18 (in the vicinity of the knee hinge joint 19) and the projectile body 2; for example, at the bottom 27 of the longitudinal recess 4.
  • the centrifugal force already acting on the inner end 21 of the rear spar 14 can be sufficient, upon rapid swinging out of the nose spar 8 from the longitudinal recess 4, to cause the rear spar 14 to deflect (rotate) rearwardly abouts its hinge pin 16 and to thereby, along with tautening of the covering 7, move the knee hinge joint 19 into its stable extended position.
  • This causes the base rib 18 to hold the spars 8, 14 spread triangularly and thus maintains the covering 7 taut.
  • FIG. 1 Shown in FIG. 1 in phantom lines is also the position of the rear spar 14 pivoted against the rear of nose spar 8; in effect, the position of the base rib 18 shown retracted (folded in). From this retracted position, the nose spar 8 can be pivoted backwardly behind the peripheral boundary of the outer wall 3 of the projectile and, along with the retraction of the covering 7 into the longitudinal recess 4; part of the base rib 18 together with knee hinge joint 19 and part of the rear spar 14 extend into the rear of the nose spar 8.
  • the rear region 22 of spar 8 is provided with a rearwardly open U-shaped cross-section, as is evident from FIG. 2.
  • the inner space 23 defined by region 22 serves to receive those upwardly pivoted parts of the strut arrangement 6, the legs 24 of the U-shape externally determine as the wing surfaces 10 the shape adopted by the covering 7 when the wing 5 is pivoted outwardly.
  • a detent for the inner end 21 of the rearwardly pivoted rear spar 14 can be provided in the rearward region of the longitudinal recess 4, proximate the outer wall 3, through which detent there can be limited the outward (extension) movement of the nose spar 8; such that irrespective of the oncoming airflow factors, there is ensured a predefined inclination of the wing leading edge 9 relative to the peripheral surface of the projectile body 2.
  • the thickness of the wing 5 in the region of its trailing edge 13 is always very narrow and also, since usually for aerodynamic reasons, the rearward wing surface 17 in contrast with the front wing surface 10 may not need to be specially profiled in a defined manner, the bracing wire 28 can then also serve for rearward fixing of the covering 7, and in effect, as shown in FIG. 3 completely replace a rear spar (14 in FIG. 1/FIG. 2) which would need to be separately hinged to the nose spar.
  • the strut arrangement 6 is provided, instead of a knee-joint base rib, with a unitary rigid rocker arm 38 which is hinged to an inner end 20 of the nose spar 8 through a hinge pin 60.
  • both the rocker arm 38 and the rear spar 14 lie within the inner space 23 which opens in a direction away from the wing leading edge 9, in effect, opens rearwardly.
  • Space 23 is located in the rearward region 22 of the nose spar 8 and is bounded by wing surface 10 in the manner of U-legs 24.
  • a traction cable 30 which is fastened to the projectile body (not shown), acts in the region of the rear end 39 on the rocker arm 38, when the nose spar 8 is pivoted from its retracted-in (folded) inoperative position parallel to the longitudinal axis of the projectile body, and thereby into an operational position.
  • rocker arm 38 is drawn at its free end 39 rearwardly out of the nose spar inner space 23, in essence pivoted rearwardly about its hinge pin 16 into parallel with the longitudinal axis of the projectile body.
  • the leading or front edge 43 of U-member 44 engages the front edge 45 of the rear spar 14 and thereby also forces spar 14 out of the rearwardly opening inner space 23 of the nose spar, along with an accompanying pivoting movement about the hinge pin 16.
  • the yoke edge 43 of the rocker-arm end 39 carries out a movement along the rear spar edge 45 in the direction of the inner end 21 thereof and towards the projectile body.
  • the inner edge 45 has a bevel 47 facing the retracted rocker arm front end 39 (FIG. 4), in order to, at the start of the deflecting movement and upon abutment of the profile edge 43, attain more favorable force-producing levering ratios.
  • the profiled edge 43 engages in a form-fitting (or snap-fit) manner into a notch 48 in the projection 46, in which the notch extends somewhat inclined oppositely to the forward direction of the edge 43 in order to assist in providing a secure detent connection; whereby yoke 44 extends somewhat in front of its edge 43 at the same inclination.
  • the wing strut arrangement in the extended condition in effect, with the covering being taut, is reliably locked, because the taut covering forces the rear spar 14 with this notch 48 in a force-locking manner against the profiled front edge 43.
  • the side walls 49 of the U-profile 41 of the rocker arm 38 protrudes beyond the yoke edge 43 in order to ensure, during the displacement of the edge 43 along the rear-spar frontward edge 45, a lateral guidance and to produce in the engaged and tightened position (FIG. 5), an additional lateral rigidity at the transition between the base rocker arm 38 and the rear spar 14.
  • the rear spar 14, when moved into the retracted (folded) position between the U-legs 49 is preferably also of U-profile shape 50 in cross-section, between the legs 51 of which there are disposed stiffening ribs 52 which extend transversely of the longitudinal direction; this representing a construction which is both lightweight while highly resistant to distortion.
  • the yoke 53 as shown in FIG. 4, is preferably rounded off at the outside in order to ensure that the covering conducted thereabout is not damaged by any sharp edges. Moreover, any overstressing of the covering is avoided in that the rearward pivoting movement of the rear spar 14 is additionally limited by an abutment shoulder 54 on the outer end 55 of the rear spar 14 in the region of the nose spar outlet end 15.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
  • Professional, Industrial, Or Sporting Protective Garments (AREA)
US06/772,247 1983-11-09 1985-09-03 Projectile having extendable wings Expired - Fee Related US4664338A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833340501 DE3340501C2 (de) 1983-11-09 1983-11-09 Geschoß mit herausklappbaren Flügeln
DE19843403573 DE3403573A1 (de) 1983-11-09 1984-02-02 Geschoss mit herausklappbaren fluegeln

Publications (1)

Publication Number Publication Date
US4664338A true US4664338A (en) 1987-05-12

Family

ID=25815486

Family Applications (1)

Application Number Title Priority Date Filing Date
US06/772,247 Expired - Fee Related US4664338A (en) 1983-11-09 1985-09-03 Projectile having extendable wings

Country Status (4)

Country Link
US (1) US4664338A (fr)
DE (1) DE3403573A1 (fr)
FR (1) FR2559893B1 (fr)
GB (1) GB2149481B (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4858851A (en) * 1988-06-07 1989-08-22 General Dynamics Pomona Division Folding wing structure for missile
US4883239A (en) * 1987-11-13 1989-11-28 Diehl Gmbh & Co. Guided artillery projectile with trajectory regulator
US4923143A (en) * 1988-11-15 1990-05-08 Diehl Gmbh & Co. Projectile having extendable wings
US5137229A (en) * 1990-05-25 1992-08-11 Diehl Gmbh & Co. Wing extendable from an airborne body
US5381986A (en) * 1992-01-30 1995-01-17 The Boeing Company Folding wing-tip system
US5452864A (en) * 1994-03-31 1995-09-26 Alliant Techsystems Inc. Electro-mechanical roll control apparatus and method
US5615846A (en) * 1994-11-04 1997-04-01 Gec Marconi Dynamics Inc. Extendable wing for guided missles and munitions
US6186443B1 (en) 1998-06-25 2001-02-13 International Dynamics Corporation Airborne vehicle having deployable wing and control surface
US6260797B1 (en) * 1998-01-13 2001-07-17 Science Applications International Corporation Transformable gun launched aero vehicle
US20080111020A1 (en) * 2006-11-14 2008-05-15 Raytheon Company Delayed tail fin deployment mechanism and method
US7841559B1 (en) 2006-02-16 2010-11-30 Mbda Incorporated Aerial vehicle with variable aspect ratio deployable wings
US20160176503A1 (en) * 2011-12-13 2016-06-23 The Boeing Company Mechanisms for Deploying and Actuating Airfoil-Shaped Bodies on Unmanned Aerial Vehicles
US10124880B1 (en) * 2016-02-03 2018-11-13 Lockheed Martin Corporation Rotatable control surface assembly for an unmanned aerial vehicle
US10583910B2 (en) 2009-09-09 2020-03-10 Aerovironment, Inc. Elevon control system
US10703506B2 (en) 2009-09-09 2020-07-07 Aerovironment, Inc. Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
US11555672B2 (en) 2009-02-02 2023-01-17 Aerovironment, Inc. Multimode unmanned aerial vehicle

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3422231A1 (de) * 1984-06-15 1985-12-19 Diehl GmbH & Co, 8500 Nürnberg Einrichtung zum aerodynamischen abbremsen der rotationsbewegung eines koerpers
GB2162623B (en) * 1984-06-15 1988-08-10 Diehl Gmbh & Co A mechanism for aerodynamic deceleration and a body including such a mechanism
DE3523769A1 (de) * 1985-07-03 1987-01-08 Diehl Gmbh & Co Submunitions-flugkoerper mit ausstellbaren gleitfluegeln
GB8815060D0 (en) * 1988-06-24 1988-11-16 British Aerospace Fin assembly for projectile
DE3918244A1 (de) * 1989-06-05 1990-12-06 Diehl Gmbh & Co Von einem flugkoerper wegklappbarer fluegel
DE102004007311A1 (de) 2004-02-14 2005-09-01 Diehl Bgt Defence Gmbh & Co. Kg Geschoss mit vom Geschoss-Rumpf wegklappbaren Flügeln

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1339188A (en) * 1918-11-20 1920-05-04 Zigmond Frecska Aerial torpedo
US3507150A (en) * 1966-01-24 1970-04-21 Robert F Stengel Wind velocity probing device and method
US3743218A (en) * 1968-06-28 1973-07-03 T Sweeney Semi-rigid airfoil for airborne vehicles
US4351499A (en) * 1979-09-24 1982-09-28 General Dynamics Double fabric, retractable, self-erecting wing for missle
US4586681A (en) * 1983-06-27 1986-05-06 General Dynamics Pomona Division Supersonic erectable fabric wings

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL90108C (fr) * 1951-11-07
DE1203647B (de) * 1962-09-11 1965-10-21 Dynamit Nobel Ag Flossenleitwerk, insbesondere fuer Raketengeschosse
US3636877A (en) * 1964-06-02 1972-01-25 Us Navy Antisubmarine missile
GB1258044A (fr) * 1967-11-02 1971-12-22
US3464356A (en) * 1967-12-28 1969-09-02 Us Army Self-stabilizing rod penetrators
FR1563898A (fr) * 1968-02-13 1969-04-18
GB1597351A (en) * 1971-06-10 1981-09-09 British Aerospace Missiles
US4364531A (en) * 1980-10-09 1982-12-21 Knoski Jerry L Attachable airfoil with movable control surface
IL66624A (en) * 1982-02-10 1986-04-29 Gen Dynamics Corp Wing housing and cover release assembly for self-erecting wing of a structure such as missile
US4586680A (en) * 1982-02-10 1986-05-06 General Dynamics Pomona Division Spring-erected telescopic wing support structure
DE3340501C2 (de) * 1983-11-09 1986-12-04 Diehl GmbH & Co, 8500 Nürnberg Geschoß mit herausklappbaren Flügeln

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1339188A (en) * 1918-11-20 1920-05-04 Zigmond Frecska Aerial torpedo
US3507150A (en) * 1966-01-24 1970-04-21 Robert F Stengel Wind velocity probing device and method
US3743218A (en) * 1968-06-28 1973-07-03 T Sweeney Semi-rigid airfoil for airborne vehicles
US4351499A (en) * 1979-09-24 1982-09-28 General Dynamics Double fabric, retractable, self-erecting wing for missle
US4586681A (en) * 1983-06-27 1986-05-06 General Dynamics Pomona Division Supersonic erectable fabric wings

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4883239A (en) * 1987-11-13 1989-11-28 Diehl Gmbh & Co. Guided artillery projectile with trajectory regulator
US4858851A (en) * 1988-06-07 1989-08-22 General Dynamics Pomona Division Folding wing structure for missile
US4923143A (en) * 1988-11-15 1990-05-08 Diehl Gmbh & Co. Projectile having extendable wings
US5137229A (en) * 1990-05-25 1992-08-11 Diehl Gmbh & Co. Wing extendable from an airborne body
US5381986A (en) * 1992-01-30 1995-01-17 The Boeing Company Folding wing-tip system
US5452864A (en) * 1994-03-31 1995-09-26 Alliant Techsystems Inc. Electro-mechanical roll control apparatus and method
US5615846A (en) * 1994-11-04 1997-04-01 Gec Marconi Dynamics Inc. Extendable wing for guided missles and munitions
US6260797B1 (en) * 1998-01-13 2001-07-17 Science Applications International Corporation Transformable gun launched aero vehicle
US6186443B1 (en) 1998-06-25 2001-02-13 International Dynamics Corporation Airborne vehicle having deployable wing and control surface
US7841559B1 (en) 2006-02-16 2010-11-30 Mbda Incorporated Aerial vehicle with variable aspect ratio deployable wings
US20080111020A1 (en) * 2006-11-14 2008-05-15 Raytheon Company Delayed tail fin deployment mechanism and method
WO2008147453A3 (fr) * 2006-11-14 2009-01-15 Raytheon Co Mécanisme et procédé de déploiement d'empennage retardé vertical
US7628353B2 (en) 2006-11-14 2009-12-08 Raytheon Company Delayed tail fin deployment mechanism and method
US11555672B2 (en) 2009-02-02 2023-01-17 Aerovironment, Inc. Multimode unmanned aerial vehicle
US12013212B2 (en) 2009-02-02 2024-06-18 Aerovironment, Inc. Multimode unmanned aerial vehicle
US20210261235A1 (en) * 2009-09-09 2021-08-26 Aerovironment, Inc. Elevon control system
US10953976B2 (en) 2009-09-09 2021-03-23 Aerovironment, Inc. Air vehicle system having deployable airfoils and rudder
US11319087B2 (en) 2009-09-09 2022-05-03 Aerovironment, Inc. Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
US10703506B2 (en) 2009-09-09 2020-07-07 Aerovironment, Inc. Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
US12103678B2 (en) * 2009-09-09 2024-10-01 Aerovironment, Inc. Elevon control system
US10960968B2 (en) * 2009-09-09 2021-03-30 Aerovironment, Inc. Elevon control system
US11040766B2 (en) 2009-09-09 2021-06-22 Aerovironment, Inc. Elevon control system
US11577818B2 (en) 2009-09-09 2023-02-14 Aerovironment, Inc. Elevon control system
US10696375B2 (en) * 2009-09-09 2020-06-30 Aerovironment, Inc. Elevon control system
US10583910B2 (en) 2009-09-09 2020-03-10 Aerovironment, Inc. Elevon control system
US12043382B2 (en) 2009-09-09 2024-07-23 Aerovironment, Inc. Elevon control system
US11667373B2 (en) * 2009-09-09 2023-06-06 Aerovironment, Inc. Elevon control system
US11731784B2 (en) 2009-09-09 2023-08-22 Aerovironment, Inc. Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
US20230264805A1 (en) * 2009-09-09 2023-08-24 Aerovironment, Inc. Elevon control system
US9533758B2 (en) * 2011-12-13 2017-01-03 The Boeing Company Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles
US20160176503A1 (en) * 2011-12-13 2016-06-23 The Boeing Company Mechanisms for Deploying and Actuating Airfoil-Shaped Bodies on Unmanned Aerial Vehicles
US10124880B1 (en) * 2016-02-03 2018-11-13 Lockheed Martin Corporation Rotatable control surface assembly for an unmanned aerial vehicle

Also Published As

Publication number Publication date
DE3403573A1 (de) 1985-08-08
GB2149481B (en) 1988-04-20
GB8428010D0 (en) 1984-12-12
FR2559893B1 (fr) 1987-10-16
FR2559893A1 (fr) 1985-08-23
GB2149481A (en) 1985-06-12

Similar Documents

Publication Publication Date Title
US4664338A (en) Projectile having extendable wings
EP0013096B1 (fr) Mécanisme pour aile repliable
US4336914A (en) Deployable wing mechanism
US4247062A (en) High efficiency vertical tail assembly combined with a variable wing geometry
US3063375A (en) Folding fin
US5857930A (en) Hunting arrow point
US5615846A (en) Extendable wing for guided missles and munitions
US4053124A (en) Variable camber airfoil
US3941334A (en) Variable camber airfoil
US5417393A (en) Rotationally mounted flexible band wing
US3994452A (en) Variable camber airfoil
US3994451A (en) Variable camber airfoil
US6152404A (en) Apparatus for influencing a wing root airflow in an aircraft
US4869442A (en) Self-deploying airfoil
US5240203A (en) Folding wing structure with a flexible cover
NO146828B (no) Vingeenhet for prosjektil
US4838502A (en) Resiliently deployable fairing for sealing an airframe cavity
US3273500A (en) Self-erecting folding fin
GB2159930A (en) Swing-wing
US4869441A (en) Subordinate-ammunition missile with extendable glide wings
US6152041A (en) Device for extending the range of guided bombs
US3790104A (en) High/low aspect ratio dual-mode fin design
KR860001011B1 (ko) 스프링-직립 신축자재날개 지지 구조물
US3690595A (en) Self-propelled, vaned missile
US5039030A (en) Wing extendable from an airborne body

Legal Events

Date Code Title Description
AS Assignment

Owner name: DIEHL GMBH & CO., STEPHANSTRASSE 49, 8500 NURNBERG

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:STEUER, RAIMAR;REEL/FRAME:004452/0321

Effective date: 19850712

FEPP Fee payment procedure

Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

FPAY Fee payment

Year of fee payment: 4

REMI Maintenance fee reminder mailed
LAPS Lapse for failure to pay maintenance fees
FP Lapsed due to failure to pay maintenance fee

Effective date: 19950517

STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362